AD 81-11-01 ACTIVE

81-11-01 GOVERNMENT AIRCRAFT FACTORIES (GAF): Amendment 39-4302. Applies to Nomad Models N22 and N24 series airplanes certificated in any category.

COMPLIANCE: Required as indicated unless already accomplished.

To assure the emergency exit can be opened when the emergency exit door handle is placed in the open position, within the next 10 hours time-in-service after the effective date of this AD, accomplish the following:

A) Visually inspect the emergency exit door for proper operation by rotating the emergency exit door handle (interior) to the open position and open the door by physically pushing outward at the bottom of the exit door. It is only necessary to move the door 0.5 inches (12 millimeters) outward to assure proper emergency door operation and that the door latch pins are fully withdrawn. Further movement of the door beyond 0.5 inches could fracture the door trim panel at the lower edge.

NOTE: Operation of the door-locking mechanism should not require undue force in complying with this paragraph.

B) If the emergency exit door opens properly in accordance with paragraph A) of this AD, secure the door in the closed position and record compliance of this AD with an appropriate entry in the airplane maintenance records.

C) If the emergency exit door handle will not rotate or the door will not open in accordance with paragraph A) of this AD, accomplish the following:

1. Remove the inner trim panel from the door in accordance with the manufacturer' s Maintenance Manual No. 25-20-00, page 201, paragraph 1B(3).

2. Visually inspect the door-locking mechanism, including linkage to door locking pins for proper assembly and also assure the door lock pins are free of corrosion and are not seized in the door frame or fuselage by performing the following as applicable:

a) Proper assembly of the door lock assembly is assured if the forward door lock pin linkage rod is almost horizontal while the rear rod is angledupwards, thus as viewed from the inside, a clockwise rotation (towards open) of the exit door handle will withdraw the door locking pins. If the linkage is incorrectly assembled, refer to the manufacturer's Illustrated Parts Catalog No. 52-20-01, Figure 1, and:

i. Disconnect both operating (linkage) rods (item 8) from the lever assembly (item12), by removing cotter pin, washer and connecting pins (items 9, 10 and 11).

ii. Rotate the door lever (handle) assembly (item 12) so that the forward end is sloping upwards at approximately 45 degrees and reconnect the linkage rods using new cotter pins.

iii. Rotate the door lever (handle) clockwise (open position) and confirm that the door lock pins can be withdrawn from the door frame and lubricate the locking pins with MIL-G-21164 grease or equivalent.

b) If the door locking pins are corroded or seized in the door frame or fuselage, free the pins, remove any corrosion and lubricate the pins with MIL-G-21164 grease or equivalent.

c) Reassemble the door and reinstall the trim panels.

D) If any part of paragraph C) of this AD was completed, reaccomplish paragraph A) of this AD to assure the emergency exit opens properly and record compliance of this AD with an appropriate entry in the airplane maintenance records.

E) Aircraft may be flown in accordance with FAR 21.197 to a location where this AD can be accomplished.

F) Any equivalent method of compliance with this AD must be approved by the Chief, Engineering and Manufacturing District Office, FAA, Pacific-Asia Region, P.O. Box 50109, Honolulu, Hawaii 96850.

GAF-Nomad Telex Alert Service Bulletin ANMD-52-2 covers the subject matter of this AD.

This amendment becomes effective on January 28, 1982, to all persons except those to whom it has already been made effective by an airmail letter from the FAA dated May 13, 1981, and identified as AD 81-11-01.